Vanes Patents (Class 415/191)
  • Patent number: 10655483
    Abstract: A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: May 19, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Martin Pernleitner, Manfred Dopfer, Marcus Woehler, Oliver Thiele, Bernd Kislinger, Norman Cleesattel, Christoph Lauer, Manfred Schill, Manuel Hein
  • Patent number: 10655502
    Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines at least one airfoil opening. At least one retention clip has an arcuate portion extending from a first elongated leg portion. The first elongated leg portion and the arcuate portion are received through the at least one airfoil opening such that the at least one retention clip limits movement of the airfoil relative to the first shroud.
    Type: Grant
    Filed: May 26, 2017
    Date of Patent: May 19, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian Barainca, Gary F. Fowler
  • Patent number: 10633989
    Abstract: A nozzle has an airfoil, and the nozzle is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between opposing walls to aerodynamically interact with a fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. A trailing edge of the airfoil deviates from an axial plane by about 0.1 degrees to about 5 degrees. A turbomachine comprising a plurality of nozzles is also provided.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: April 28, 2020
    Assignee: General Electric Company
    Inventors: Shashwat Swami Jaiswal, Rohit Chouhan, Lukasz Szajko
  • Patent number: 10619497
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: April 14, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Pascal Pierre Nicolas Routier, Jean-Armand Marc Emilien Destouches, Thomas Michel Julien Mervant, Ludovic Pintat, Guillaume Jochen Scholl
  • Patent number: 10619496
    Abstract: A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow. A hollow within the airfoil extends between an inner leading edge to an inner trailing edge. An inner radius is defined at the inner trailing edge in a circumferential direction measured between walls which extend from the inner leading edge to the inner trailing edge. The inner radius varies along a radial length defined between the inner and outer platforms. A mid-turbine frame and a gas turbine engine are also disclosed.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: April 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Steven D. Porter, John T. Ols
  • Patent number: 10612563
    Abstract: An air conditioner comprises a compressor to compress a refrigerant, a heat exchanger to move heat of the refrigerant, and a blower to blow air. The blower comprises a fan rotatable about a rotation axis, and a plurality of stationary blades installed to be a radial shape about the rotation axis in a direction in which the airflow generated by the rotation of the fan is discharged, and are curved in a direction opposite to the rotation direction of the fan from an inner circumferential portion to an outer circumferential portion. The stationary blades comprise an inlet edge, and an outlet edge, and an inlet angle formed by the inlet edge and the rotation axis and a chord angle formed by a chord connecting the inlet edge and the outlet edge and the rotation axis are larger at the inner and outer circumferential portions than at a radial center portion.
    Type: Grant
    Filed: July 10, 2015
    Date of Patent: April 7, 2020
    Assignee: SAMSUNG ELECTRONICS CO., LTD.
    Inventor: Seiji Sato
  • Patent number: 10590782
    Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately ?0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: March 17, 2020
    Assignee: CHROMALLOY GAS TURBINE LLC
    Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, Daniel Folkers
  • Patent number: 10590954
    Abstract: The invention relates to a flow-conducting grille designed as a pre-conducting grille for arranging on a suction region of a fan, wherein the flow-conducting grille has a grille web structure about an axial center line, which grille web structure comprises radial webs spaced apart in the circumferential direction and coaxial circumferential webs spaced apart in the radial direction and an outer ring, wherein an inflow side of the flow-conducting grille extends flat and parallel to a radial plane of the flow-conducting grille.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: March 17, 2020
    Assignee: ebm-papst Mulfingen GmbH & Co. KG
    Inventors: Zhang Binyuan, Christian Haag, Carsten Hübner, Björn Sudler, Manuel Vogel
  • Patent number: 10583932
    Abstract: A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio is: the ? ? turbine ? ? diameter ? ? at ? ? an ? ? axial location ? ? of ? ? the ? ? lowest ? ? pressure ? ? rotor ? ? stage ? ground ? ? plane ? ? to ? ? wing ? ? distance and a quasi-non-dimensional mass flow rate Q defined as: Q = W ? T ? ? 0 P ? ? 0 · A flow where: W is mass flow rate through the fan in Kg/s; T0 is average stagnation temperature of the air at the fan face in Kelvin; P0 is average stagnation pressure of the air at the fan face in Pa; and Aflow is the flow area of the fan face in m2, and wherein a Q ratio of: the downstream blockage ratio×Q is in a range from 0.005 to 0.01.
    Type: Grant
    Filed: April 30, 2019
    Date of Patent: March 10, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Richard G Stretton, Michael C Willmot
  • Patent number: 10577937
    Abstract: A fan blade is provided with an aerofoil portion for which, for cross-sections through the aerofoil portion at radii between 15% and 25% of the blade span from the root radius, the average leading edge thickness is greater than the leading edge thickness at the tip. The geometry of the fan blade may result in a lower susceptibility to flutter.
    Type: Grant
    Filed: February 12, 2018
    Date of Patent: March 3, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Mark J. Wilson, Gabriel Gonzalez-Gutierrez, Marco Barale, Benedict Phelps, Kashmir S. Johal, Nigel H S Smith
  • Patent number: 10577938
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: March 3, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Thomas Michel Julien Mervant, Vincent Nicolas Leonardon, Pierre Hervé Fernand Marche, Pascal Pierre Nicolas Routier, Ludovic Pintat
  • Patent number: 10577953
    Abstract: A stator vane is comprised of: an airfoil section elongated in a radial direction relative to an axis; an outer band section continuous to an outer end of the airfoil section and bent in a circumferential direction relative to the axis; a first hook section continuous to a leading end in the axial direction of the outer band section and bent outward in the radial direction; a second hook section continuous to a trailing end in the axial direction of the outer band section and bent outward in the radial direction; an inner band section continuous to an inner end of the airfoil section and bent in the circumferential direction; a flange section continuous to an end in the axial direction of the inner band section and bent inward in the radial direction; and a reinforcement fiber fabric continuous throughout these sections and unitized with a ceramic.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: March 3, 2020
    Assignee: IHI Corporation
    Inventor: Fumiaki Watanabe
  • Patent number: 10570767
    Abstract: An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: February 25, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Russell Ratzlaff, Ronald Scott Bunker
  • Patent number: 10563669
    Abstract: A fan includes an impeller including a boss that is a rotation center, and a plurality of blades that are provided on an outer peripheral surface of the boss; a motor and a motor fixing portion rotationally driving the impeller; a housing accommodating the impeller; a plurality of stationary blades disposed downstream of the impeller and connecting the motor fixing and the housing; and a connecting portion disposed between the housing and a rotation axis of the impeller, and extending in a rotation direction of the impeller and connecting the plurality of stationary blades. The connecting portion has a recessed portion for passing wind that flows in a radial direction of the impeller.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: February 18, 2020
    Assignee: Mitsubishi Electric Corporation
    Inventors: Kenichi Sakoda, Tomoya Fukui, Masayuki Oishi
  • Patent number: 10533452
    Abstract: An acoustic damper includes a housing with an inlet aperture and an outlet aperture. The housing is configured to receive a gas flow that enters via the inlet aperture and that exits via the outlet aperture. The acoustic damper also includes a barrier member that is disposed within the housing. The barrier member is configured to be disposed within the gas flow and to dampen acoustic energy that propagates in an upstream direction generally from the outlet aperture toward the inlet aperture. The barrier member includes an outer structure that defines an interior volume of the barrier member. The interior volume is oriented toward the outlet aperture.
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: January 14, 2020
    Assignee: GARRETT TRANSPORTATION I INC.
    Inventors: Bhushan Singh Gautam, Gladys Gaude
  • Patent number: 10526895
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: January 7, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Vincent Nicolas Leonardon, Thomas Michel Julien Mervant, Guillaume Jochen Scholl, Ludovic Pintat, Renaud Gabriel Constant Royan
  • Patent number: 10508550
    Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: December 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Loubriel Ramirez
  • Patent number: 10508559
    Abstract: A fiber preform for a turbine engine blade or vane obtained by single-piece three-dimensional weaving. The preform includes a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.
    Type: Grant
    Filed: November 12, 2013
    Date of Patent: December 17, 2019
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Matthieu Gimat, Dominique Marie Christian Coupe
  • Patent number: 10480531
    Abstract: An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: November 19, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Takanori Shibata, Naoto Omura, Chihiro Myoren, Yasuo Takahashi
  • Patent number: 10465559
    Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform has a gas path side that supports the radially outer end of the at least one airfoil and a non-gas path side. A hook is supported by the platform and has an anti-rotation surface that faces in a circumferential direction. A conical surface is spaced axially forward of a base portion of the hook. A triangular base surface intersects the anti-rotation surface and is spaced radially outward from the conical surface.
    Type: Grant
    Filed: December 13, 2017
    Date of Patent: November 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ky H. Vu, Bryan P. Dube, Michael J. Allen
  • Patent number: 10458245
    Abstract: When cold and in the non-coated state, a turbine blade includes an aerodynamic profile that is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: October 29, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Pierre Routier, Vincent Nicolas Leonardon, Daniel Marius Man, Pierre Hervé Marche
  • Patent number: 10458246
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: October 29, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Thomas Michel Mervant, Erwan Daniel Botrel, Maxime Didier Delabriere, Jean-Armand Marc Destouches
  • Patent number: 10415406
    Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: May 3, 2017
    Date of Patent: September 17, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Neil Ristau, Russell DeForest, Frederic Woodrow Roberts, Jr.
  • Patent number: 10408227
    Abstract: The present disclosure is directed toward airfoils used in gas turbine engines. More specifically, the present disclosure teaches airfoils with fillets for managing stresses in airfoils during use in gas turbine engines.
    Type: Grant
    Filed: July 13, 2016
    Date of Patent: September 10, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Patrick E. Bailey, Timothy Unton
  • Patent number: 10352330
    Abstract: A turbomachine part including at least first and second blades, and a platform from which the blades extend, wherein the platform has a non-axisymmetric surface limited by first and second end planes, and defined by at least three construction curves of class CI each representing the value of a radius of the surface on the basis of a position between the lower surface of the first blade and the upper surface of the second blade according to a plane substantially parallel to the end planes, including a first curve that increases in the vicinity of the second blade; a second curve that decreases in the vicinity of the second blade; a third curve having a minimum at the second blade.
    Type: Grant
    Filed: October 10, 2014
    Date of Patent: July 16, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Damien Joseph Cellier
  • Patent number: 10329914
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: June 25, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Daniel Marius Man, Maxime Didier Delabriere, Pierre Hervé Marche, Pascal Pierre Routier
  • Patent number: 10309419
    Abstract: A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.
    Type: Grant
    Filed: October 11, 2012
    Date of Patent: June 4, 2019
    Assignee: SAFRAN AIRCARFT ENGINES
    Inventors: Damien Cellier, Alicia Lise Julia Dufresne, Philippe Pierre Marcel Marie Pelletrau, Vincent Paul Gabriel Perrot, Jean-Francois Antoine Christian Rios, Laurent Christophe Francis Villaines
  • Patent number: 10301944
    Abstract: A cast turbine blade having a platform and hollow blade airfoil arranged thereon, wherein the blade airfoil has a pressure-side blade wall and a suction-side blade wall that extend, along a centrally arranged curved profile centerline, from a common leading edge to a common trailing edge, and having a transition, with an outer contour profile, between the blade airfoil and the platform. The blade walls each have a locally determined blade wall thickness, wherein the turbine blade has, internally, a contour profile that partially matches the outer contour profile of the transition such that the region of the transition has an essentially constant blade wall thickness. In the transition, the contour profile at a surface section of the blade airfoil facing the leading edge is such that the blade wall thickness is increased there in comparison to the blade wall thickness of the transition away from the leading edge.
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: May 28, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Björn Buchholz, Ralph Gossilin, Daniela Koch, Marco Schüler
  • Patent number: 10294796
    Abstract: A blade or vane arrangement for a gas turbine engine has an array of aerofoils mounted to respective platforms about an axis and defining a passage through which a working gas flow passes. The arrangement has a datum and the aerofoil has a radial span. Each aerofoil has pressure side, a suction side, a leading edge region and a leading edge foot extending from the leading edge region, the leading edge foot has a ridge line. The platform defines a channel and a platform leading edge, the channel has a minimum radial height line, and the platform leading edge partly defines an outlet through which a secondary flow passes. The ridge line is aligned generally in the direction of the working gas flow and the minimum radial height line is aligned generally in the direction of the secondary flow.
    Type: Grant
    Filed: July 29, 2014
    Date of Patent: May 21, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Yan Sheng Li, Roy Teuber
  • Patent number: 10287889
    Abstract: A power turbine includes a first stage vane having an airfoil with a cold nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 26, 2017
    Date of Patent: May 14, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Niloofar Moradi
  • Patent number: 10288086
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Moorthi Subramaniyan, John David Dyer
  • Patent number: 10280777
    Abstract: A method and system including a circumferential seal assembly for sealing between components within a turbine is provided. A circumferential seal assembly is disposed in a slot extending circumferentially about an inner barrel. The seal assembly includes a first shim layer and at least one additional shim layer configured in an overlapping stacked configuration so as to stagger the end portions of each of the shim segments defined by the shim layers, relative to one another and circumferentially about the seal assembly. One or more cloth layers are configured wrapping about the first shim layer and the at least one additional shim layer to define a sealing member having a first sealing surface and a second sealing surface. The assembly further including a base plate, wherein the sealing member is disposed on an upper surface of the base plate to provide for sealing engagement between the components of the turbine.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: May 7, 2019
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Norman Arnold Turnquist, Christopher Edward Wolfe
  • Patent number: 10280774
    Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: May 3, 2017
    Date of Patent: May 7, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: John Franklin Ryman, Victor John Morgan, Mary Virginia Holloway
  • Patent number: 10267158
    Abstract: The present disclosure includes airfoils for use in gas turbine engines. The airfoils comprise a fillet having a height of greater than 20% of the airfoil body span length. The airfoil may be a blade or a vane. Further, such airfoils may be used in the high pressure compressor section, as well as other gas turbine engine sections.
    Type: Grant
    Filed: September 23, 2015
    Date of Patent: April 23, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Potter, Michael Espinoza, Joseph Steele
  • Patent number: 10260362
    Abstract: A turbine vane for a gas turbine engine incorporating a ceramic matrix composite airfoil is disclosed in this paper. The turbine vane includes an attachment unit configured to mount the ceramic matrix composite airfoil to other metallic components of the turbine vane.
    Type: Grant
    Filed: May 30, 2017
    Date of Patent: April 16, 2019
    Assignee: Rolls-Royce Corporation
    Inventor: Bruce E. Varney
  • Patent number: 10240578
    Abstract: An erosion resistant aerodynamic fairing for a rotor blade. A fairing body is formed from at least one reinforcing fiber layer set in a cured resin. An erosion resistant pre-form is fixed to an outer surface of the fairing body. The erosion resistant pre-form comprises a thermoplastic film outer layer fused to a fiber substrate. The fiber substrate of the erosion resistant pre-form is impregnated with the cured resin of the fairing body which fixes at the preform to the fairing body.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: March 26, 2019
    Assignee: BLADE DYNAMICS LIMITED
    Inventors: Harald Behmer, Peter Anthony Broome, Paul Trevor Hayden
  • Patent number: 10221710
    Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: March 5, 2019
    Assignee: General Electric Company
    Inventors: Aaron Gregory Winn, George Andrew Gergely, Mary Virginia Holloway, Paul Kendall Smith
  • Patent number: 10215041
    Abstract: A sealing ring segment for a stator of a turbine, the sealing ring segment has substantially the shape of a cylinder casing segment and has on its outer side a groove for fixing a plurality of guide vanes. The sealing ring segment has, for each guide vane that is fixable to the sealing ring segment, at least one pressure bolt that acts on the respective guide vane by a restoring force, the pressure bolt being able to be fixed and accordingly oriented by a corresponding opening in the sealing ring segment and being configured as a cylindrical element which can be compressed in the axial direction, and wherein the respective pressure bolt has a disk spring and the restoring force of the respective pressure bolt acts in the radial direction with respect to the rotation axis of the turbine in which the sealing ring segment is placed.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: February 26, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Thorsten Barz, Roland Habel, Sebastian Stupariu-Cohan
  • Patent number: 10190417
    Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: January 29, 2019
    Assignee: General Electric Company
    Inventors: Lee Larned Brozyna, Mehmet Suleyman Ciray, Mark Andrew Jones
  • Patent number: 10180073
    Abstract: A turbine nozzle includes an arcuate inner band having opposed flowpath and back sides, and an aft flange extending outward from the back side; an arcuate outer band having opposed flowpath and back sides; an airfoil-shaped turbine vane extending between the flowpath sides of the inner and outer bands, wherein the inner and outer bands and the vane comprise a ceramic low-ductility material; and a metallic collar surrounding the aft flange.
    Type: Grant
    Filed: August 6, 2014
    Date of Patent: January 15, 2019
    Assignee: General Electric Company
    Inventors: Michael Ray Tuertscher, Darrell Glenn Senile, Greg Phelps
  • Patent number: 10119410
    Abstract: A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: November 6, 2018
    Assignee: United Technologies Corporation
    Inventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
  • Patent number: 10077676
    Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A trailing edge full span flap is removable secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface where the full span flap minimizes vortex shedding of the fluid flow from the tangential strut.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: September 18, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Yevgeniy P. Shteyman, John Giaimo, Randy Tindell
  • Patent number: 10066641
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: October 5, 2016
    Date of Patent: September 4, 2018
    Assignee: General Electric Company
    Inventors: Prabakaran Modachur Krishnan, Dwight Eric Davidson, Nandakumar Aladahalli Rangaswamy
  • Patent number: 10041503
    Abstract: A system is provided, including an airfoil. The an airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 30, 2016
    Date of Patent: August 7, 2018
    Assignee: General Electric Company
    Inventors: Matthew John McKeever, Sharan Shanti
  • Patent number: 10018060
    Abstract: A computer-based method of designing a guide vane formation is provided. The vane formation is for use in a gas turbine engine which has a cascade of circumferentially arranged identical guide vane formations. The vane formation has radially inner and radially outer chordal seals. The method allows the elimination of “saw-tooth” leakage gaps between inner chordal seals of neighboring vane formations and between outer chordal seals of neighboring vane formations even when the inner and outer chordal seals are axially offset from each other.
    Type: Grant
    Filed: March 18, 2015
    Date of Patent: July 10, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Caner Hasan Helvaci, Brian Guy Cooper
  • Patent number: 10012086
    Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to +0.050 inches (+1.27 mm).
    Type: Grant
    Filed: November 4, 2014
    Date of Patent: July 3, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David M. Pons, Loubriel Ramirez
  • Patent number: 10006356
    Abstract: Methods and systems are provided for an adjustable diffuser of a turbocharger compressor. In one example, a compressor includes a diffuser formed in a compressor housing downstream of an impeller of the compressor, the diffuser including guide blades mounted on a rotatable annular support of the diffuser. Further, an engine controller may adjust rotation of the annular support based on one or more engine operating conditions.
    Type: Grant
    Filed: February 19, 2016
    Date of Patent: June 26, 2018
    Assignee: Ford Global Technologies, LLC
    Inventors: Joerg Kemmerling, Helmut Matthias Kindl, Vanco Smiljanovski, Franz Arnd Sommerhoff, Andreas Kuske, Frank Wunderlich
  • Patent number: 9982548
    Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: May 29, 2018
    Assignee: United Technologies Corporation
    Inventors: John T. Ols, Karl A. Mentz, Richard N. Allen, Steven D. Porter, Renee J. Jurek, Paul K. Sanchez, Sandra S. Pinero
  • Patent number: 9932886
    Abstract: A turbocharger has an annular bypass valve disposed in an annular portion of a bypass passage of the turbine housing. The turbine housing defines an exhaust gas chamber having separate half-annular first and second scrolls, and a portion of the bypass passage is sector-divided by a pair of dividing walls that create two 180-degree bypass sectors respectively connected to the first and second scrolls. Each dividing wall has a through-hole. The valve rotor defines a pair of valve members that close the through-holes when the bypass valve is fully closed. When the valve rotor begins to rotate toward an open position, first the valve members open the through-holes to connect the two bypass sectors, and then the bypass flow passages begin to open.
    Type: Grant
    Filed: February 17, 2016
    Date of Patent: April 3, 2018
    Assignee: Honeywell International Inc.
    Inventors: Alain Lombard, Lionel Toussaint, Chris Groves, Aurelien Tingaud
  • Patent number: 9932848
    Abstract: A power turbine unit includes a turbine housing, an exhaust duct, a turbine wheel with blades positioned in the exhaust duct, a shaft rigidly connected to the turbine wheel and rotatably supported in the housing, and an oil sealing system. The oil sealing system includes a sealing arrangement positioned in the vicinity of the turbine wheel for preventing oil from escaping from the turbine housing along the shaft to the exhaust duct. The oil sealing system further includes a buffer gas duct that is arranged to supply exhaust gas from the exhaust duct to the sealing arrangement for pressurizing the sealing arrangement.
    Type: Grant
    Filed: November 21, 2012
    Date of Patent: April 3, 2018
    Assignee: Volvo Truck Corporation
    Inventors: Kent Giselmo, Magnus Ekstrand, Lars Sundin, Sebastian Krausche